Viscous flow and performance issues in a 6:1 supersonic mixed-flow compressor with a tandem diffuser

Sadagopan, Aravinth; Camcı, Cengiz

doi:10.1016/j.ast.2019.02.027

Cited by 6 publications

(3 citation statements)

References 6 publications

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“…The dimensionless quantity Ω gas_air is more complex but usually of an order of one [26]. The detailed calculation is affected by the interaction between the two species [29].…”

Section: Lifting Gas Diffusion Modelmentioning

confidence: 99%

Effect of Lifting Gas Diffusion on the Station-Keeping Performance of a Near-Space Aerostat

Ling

Lei

et al. 2022

Aerospace

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During the long-endurance flight of a near-space aerostat, the characteristics of lifting gas diffusion have a great influence on the flight altitude adjustment and station-keeping performance. Thus, in this study, a lifting gas diffusion model and a dynamic model that consider thermal effects, which had not been studied in similar models before, were developed. The dynamic model and thermal model were validated by historic flight data, and the calculated lifting gas diffusion results were compared with the experimental data of other researchers. The variations in the flight endurance, flight altitude, lifting gas diffusion rate, and diffusion coefficient of a near-space aerostat were analyzed. The effects of the ratio of porosity to tortuosity and envelope radiation properties on the mass of the lifting gas and flight altitude were considered in detail. To analyze the effect mechanism of the ratio of porosity to tortuosity and the envelope radiation properties, the envelope and gas temperature, as well as the gas pressure, were studied. The results show that the lifting gas diffusion rate and diffusion coefficient are very sensitive to the change in the ratio of porosity to tortuosity and envelope temperature. The results obtained from the analysis of the lifting gas diffusion can lay a solid foundation for improving the flight performance of near-space aerostats and for providing improved design considerations for aerostats.

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“…The dimensionless quantity Ω gas_air is more complex but usually of an order of one [26]. The detailed calculation is affected by the interaction between the two species [29].…”

Section: Lifting Gas Diffusion Modelmentioning

confidence: 99%

Effect of Lifting Gas Diffusion on the Station-Keeping Performance of a Near-Space Aerostat

Ling

Lei

et al. 2022

Aerospace

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“…This range was selected based on the relatively well performing mixed flow compressors developed by Giri et al (2016), Kock (2017) and Sadagopan and Camci (2019a) for a similar operating mass flow rate. The lower bound for α z2 was chosen based on the research of Sadagopan and Camci (2019b), which suggests that more axial designs are not likely to attain the desired pressure ratio requirements in a single (compact) stage.…”

Section: Design Type Choicesmentioning

confidence: 99%

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Ochabski

Spuy

Hildebrandt³

2020

Volume 8: Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Microturbines, Turbochargers, and Small

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A parametrization method for the simultaneous optimization of the impeller and diffuser of a mixed flow compressor stage across a wide geometrical diversity is presented. The optimization focused on determining the optimal mixed flow (meridional) angle for a predefined set of constraints. The number of parameters required to achieve the large geometric diversity associated with a variable mixed flow angle was greatly reduced by coupling the endwall and camber Bézier control points with user-defined functions. The influence of geometric features on design performance was assessed using a Pearson correlation coefficient map. It was observed that stage total-to-static pressure ratio, and efficiency, were strongly influenced by diffuser outlet passage height and diffuser vane wrap angle. This was due to these parameters’ control of flow separation magnitude at the diffuser hub in the radial-to-axial bend. The method improved design point efficiency by 4.24 percentage points (to 86.24%) and increased the operating range by 6.7% at the cost of a decreased design point pressure rise, when compared to the baseline design.

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“…They described a new tandem design supersonic diffuser. They stated that this new design outperformed previous supersonic diffusion configurations by 20% in terms of efficiency [26]. Cravero et al simulated a two-stage back-to-back radial compressor for refrigerant applications using computational fluid dynamics techniques at operating points close to the surge point.…”

Section: Introductionmentioning

confidence: 99%

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

Soylemez,

Behçet,

Parlak

2024

Applied Sciences

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Centrifugal compressors are frequently used in both military and commercial areas because they can be easily manufactured and reach high-pressure compression ratios. The factor that limits the performance and operating range of compressors is flow instability. Many ideas have been put forward for performance improvement, but tandem blade radial compressors, which do not require an extra air system, have attracted the most interest. In this study, computational fluid dynamics (CFD) analyses were carried out on various parameters of the tandem blade (TB) radial compressor, and an optimization study was carried out to find the best design using a genetic algorithm on a whole operating curve. It was investigated how these parameters affected the efficiency and total pressure ratio between the determined lower and upper limits. The numerical analyses of the optimum design obtained as a result of the iterations were carried out. As a result of the iterations, three optimum designs were obtained and numerical analysis was carried out according to one of them, and then they were compared with the results in the literature. The general agreement of computational fluid dynamics and the literature data served as a validation for the computational approach. The error rates between the numerical analysis results and the experimental results in the literature were calculated for different flow rates and were found to be 1.98% as the highest and 0.35 as the lowest. The work carried out in this article will provide a valuable reference for future advanced tandem blade compressor designs.

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Viscous flow and performance issues in a 6:1 supersonic mixed-flow compressor with a tandem diffuser

Cited by 6 publications

References 6 publications

Effect of Lifting Gas Diffusion on the Station-Keeping Performance of a Near-Space Aerostat

Effect of Lifting Gas Diffusion on the Station-Keeping Performance of a Near-Space Aerostat

A Large Design Space Multidisciplinary Optimization of a Mixed Flow Micro Gas Turbine Compressor Stage

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

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